JP2017525826A - Molding material and method for forming the same - Google Patents
Molding material and method for forming the same Download PDFInfo
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- JP2017525826A JP2017525826A JP2017511851A JP2017511851A JP2017525826A JP 2017525826 A JP2017525826 A JP 2017525826A JP 2017511851 A JP2017511851 A JP 2017511851A JP 2017511851 A JP2017511851 A JP 2017511851A JP 2017525826 A JP2017525826 A JP 2017525826A
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- 238000000034 method Methods 0.000 title claims abstract description 36
- 239000012778 molding material Substances 0.000 title 1
- 229920005989 resin Polymers 0.000 claims abstract description 50
- 239000011347 resin Substances 0.000 claims abstract description 50
- 239000011159 matrix material Substances 0.000 claims abstract description 30
- 239000002131 composite material Substances 0.000 claims abstract description 15
- 239000012783 reinforcing fiber Substances 0.000 claims abstract description 11
- 238000011282 treatment Methods 0.000 claims description 19
- 239000000835 fiber Substances 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 8
- 238000001816 cooling Methods 0.000 claims description 6
- 238000005452 bending Methods 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 239000010410 layer Substances 0.000 description 12
- 238000000926 separation method Methods 0.000 description 7
- 239000003677 Sheet moulding compound Substances 0.000 description 3
- 239000003822 epoxy resin Substances 0.000 description 3
- 229920000647 polyepoxide Polymers 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000012779 reinforcing material Substances 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 239000002759 woven fabric Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 230000009477 glass transition Effects 0.000 description 1
- 238000005470 impregnation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 229920001169 thermoplastic Polymers 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 239000004634 thermosetting polymer Substances 0.000 description 1
- 239000004416 thermosoftening plastic Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B13/00—Conditioning or physical treatment of the material to be shaped
- B29B13/04—Conditioning or physical treatment of the material to be shaped by cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/16—Cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
Abstract
互いに接触する複数の要素（１２）を含む複合材料スタックを分離する方法が開示される。各要素（１２）は、強化繊維および未硬化樹脂マトリックスを含み、方法は、スタックを温度処理する、および／またはスタックに応力を加えて要素を分離するステップを含む。【選択図】図１A method of separating a composite stack comprising a plurality of elements (12) in contact with each other is disclosed. Each element (12) includes a reinforcing fiber and an uncured resin matrix, and the method includes the steps of temperature treating the stack and / or applying stress to the stack to separate the elements. [Selection] Figure 1
Description
本発明は、複合材料を分離する方法、並びに分離された複合材料、成形体および複合要素に関し、特に、しかしそれだけではないが、複合材料スタック（ｓｔａｃｋ）を分離する方法に関する。 The present invention relates to a method for separating composite materials, and to separated composite materials, shaped bodies and composite elements, and in particular, but not exclusively, to a method for separating composite stacks.
樹脂強化材料を含む複合材料、特に繊維および熱硬化樹脂を含むプリプレグは、積み重ねられてプリフォームを形成し得る。これらのプリフォームは、その後硬化されて、強化複合材料を形成する。そのような複合材料は公知であり、それらは軽量で強度が高く、自動車および航空宇宙産業などの多くの構造用途および翼を作るために使用されるスパーおよびシェルなどの風力タービン部品などの産業用途に使用される。 Composite materials including resin reinforced materials, particularly prepregs including fibers and thermoset resins, can be stacked to form a preform. These preforms are then cured to form a reinforced composite material. Such composite materials are well known and they are lightweight and strong, many structural applications such as the automotive and aerospace industries and industrial applications such as wind turbine components such as spar and shell used to make wings Used for.
プリプレグは、未硬化状態で、および硬化の準備のために、樹脂で含浸される繊維および織物を記載するために使用される用語である。繊維は、トウ（ｔｏｗ）または織物であってもよい。トウまたは織物は、一般的に、フィラメントと呼ばれる複数の細い繊維を含む。プリプレグで使用される繊維状材料および樹脂の選択は、硬化複合材料の要求される特性、また複合材料を使用する用途に依存する。 Pre-preg is a term used to describe fibers and fabrics that are impregnated with resin in the uncured state and in preparation for curing. The fiber may be a tow or a woven fabric. A tow or woven fabric typically includes a plurality of thin fibers called filaments. The choice of fibrous material and resin used in the prepreg depends on the required properties of the cured composite and the application in which the composite is used.
様々な方法がプリプレグの製造のために提案されてり、好ましい方法の１つは、液体、溶融または半固体の未硬化熱硬化性樹脂による、動いている繊維状ウェブの含浸である。次に、この方法によって製造されるプリプレグは、所望の寸法のセクションに切断され、セクションのスタックは、加熱によって硬化されて、最終的な繊維強化積層体を製造する。硬化は、翼およびスパーのためのシェルなどの風力エネルギー構造の製造において好ましいように硬化のための金型に配置され得る真空バッグ内で行われ得る。あるいは、スタックは、閉じられた金型で圧縮によって形成され、加熱によって金型で直接硬化され得る（圧縮成形）。 Various methods have been proposed for the production of prepregs and one preferred method is impregnation of a moving fibrous web with a liquid, molten or semi-solid uncured thermosetting resin. The prepreg produced by this method is then cut into sections of the desired dimensions and the stack of sections is cured by heating to produce the final fiber reinforced laminate. Curing can be performed in a vacuum bag that can be placed in a mold for curing as preferred in the manufacture of wind energy structures such as shells for wings and spars. Alternatively, the stack can be formed by compression with a closed mold and cured directly on the mold by heating (compression molding).
そのような応用で使用のための樹脂の１つの好ましいファミリーは、硬化性エポキシ樹脂および硬化剤であり、硬化剤は、通常、樹脂に含まれており、硬化サイクル時間を短縮する。エポキシ樹脂は、非常に適切な樹脂であるが、それらは、硬化後に脆くなり、衝撃の際に最終積層体に割れまたは割れ目を生じさせることがあり、したがって、エポキシ樹脂中に熱可塑性樹脂またはゴムなどの強化材料を含めることが一般的な慣行である。 One preferred family of resins for use in such applications are curable epoxy resins and curing agents, which are usually included in the resin to shorten the cure cycle time. Epoxy resins are very suitable resins, but they become brittle after curing and can cause cracks or cracks in the final laminate upon impact, and therefore thermoplastic or rubber in the epoxy resin. It is common practice to include reinforcing materials such as.
プリプレグは、強化材料の一体化層の形態であることができ、またはそれは、ランダムな方向に配向される要素の形態であり、準等方性材料層を形成することができる。複数のプリプレグ層または要素は、従来は、組み合わせられて、複合積層体構造を形成する。プリプレグ層は、平行に、面内方向のランダム（準等方性）に、または等方性に若しくは準等方性プリプレグ要素として、配置され得る。 The prepreg can be in the form of an integral layer of reinforcing material, or it can be in the form of an element oriented in a random direction to form a quasi-isotropic material layer. Multiple prepreg layers or elements are conventionally combined to form a composite laminate structure. The prepreg layers can be arranged in parallel, randomly in the in-plane direction (quasi-isotropic), or isotropic or as a quasi-isotropic prepreg element.
積層体の形成に続いて、それを切断し得る。これは、切断品を生成する。しかしながら、他の目的のための切断品の利用は、積層体の構成が特定の目的または用途に合わせて調整されるので、問題を有する。再使用の機会を増やすために、積層体の複数のプレプレグ層または要素への分離が望ましい。また、積層体プレフォームの分離は、一般的に、望ましく、再加工または再使用されることを可能にする。 Following formation of the laminate, it can be cut. This produces a cut product. However, the use of cuts for other purposes is problematic because the configuration of the laminate is tailored to a particular purpose or application. Separation of the laminate into multiple prepreg layers or elements is desirable to increase the opportunity for reuse. Also, separation of the laminate preform is generally desirable and allows it to be reworked or reused.
本発明は、上記の問題を回避および／または軽減し、および／または一般的に改善を提供することを目的とする。 The present invention aims to avoid and / or alleviate the above problems and / or provide improvements in general.
本発明によると、添付の特許請求の範囲のいずれか１項に定義されるように、方法、成形体、成形複合体および要素を提供する。 According to the present invention, there are provided methods, shaped bodies, shaped composites and elements as defined in any one of the appended claims.
本発明の１つの態様において、互いに接触する複数の要素を含む複合材料スタックを分離する方法を提供し、各要素は強化繊維および樹脂マトリックスを含み、ここで該方法は、スタックを温度処理するおよびスタックに応力を加えて要素を分離するステップを含む。 In one aspect of the invention, a method for separating a composite stack comprising a plurality of elements in contact with each other is provided, each element comprising a reinforcing fiber and a resin matrix, wherein the method comprises temperature treating the stack and Stressing the stack to separate the elements.
温度処理およびスタックに加えられた応力または力の組み合わせは、組み合わせられる要素および／または個々の要素の分離をもたらす。組み合わせられた要素は、さらなる温度処理および／または応力に供されて、組み合わせられた要素を個々の要素または組み合わせられる要素にさらに分離し得る。 The combination of temperature treatment and stress or force applied to the stack results in separation of the combined elements and / or individual elements. The combined elements can be subjected to further temperature treatments and / or stresses to further separate the combined elements into individual elements or combined elements.
応力が、以下の応力の１つ以上から選択され得る：
ａ．曲げ応力
ｂ．ねじり応力
ｃ．圧縮応力
ｄ．せん断応力
ｅ．剥離応力
ｆ．引張応力、および
ｇ．振動応力。
The stress may be selected from one or more of the following stresses:
a. Bending stress b. Torsional stress c. Compressive stress d. Shear stress e. Peel stress f. Tensile stress, and g. Vibration stress.
１つの態様において、曲げ応力は、要素が互いに対して曲がることを可能にする応力の印加である。ねじり応力は、要素が互いに対して回転することを可能にする応力である。圧縮応力は、要素が互いに対して圧縮されることを可能にする応力である。せん断応力は、要素が互いに対して滑らせるまたはせん断することを可能にする応力である。剥離応力は、要素が互いに対して剥がれることを可能にする応力である。引張応力は、要素が互いに対して伸ばされることを可能にする応力である。振動応力は、要素に振動を与えている。 In one aspect, bending stress is the application of stress that allows the elements to bend relative to each other. Torsional stress is the stress that allows the elements to rotate relative to each other. Compressive stress is the stress that allows the elements to be compressed against each other. Shear stress is the stress that allows the elements to slide or shear relative to each other. Peel stress is the stress that allows the elements to peel against each other. Tensile stress is the stress that allows the elements to be stretched relative to each other. Vibration stress imparts vibration to the element.
好ましい態様において、加えられる応力は、上記に列挙した応力ａ〜ｇの２つ以上の組み合わせを含む。応力は、スタック、個々の要素、組み合わせられる要素および／またはそれらの組み合わせに対して１つ以上の方向で印加され得る。これは、要素が正常に分離されることを可能にする。 In preferred embodiments, the applied stress comprises a combination of two or more of the stresses a-g listed above. The stress can be applied in one or more directions to the stack, individual elements, combined elements and / or combinations thereof. This allows the elements to be successfully separated.
要素は、好ましくは、積層体スタックを形成するように互いに平行に配置される。応力ａ〜ｆは、好ましくは、積層体スタックに対して垂直な方向で加えられる。このようにして、応力は、組み合わせられる要素および／または個々の要素に対して垂直に働く。振動応力ｇは、好ましくは、積層体または組み合わせられる要素および／または個々の要素に平行な方向で印加される。 The elements are preferably arranged parallel to each other so as to form a laminate stack. The stresses a to f are preferably applied in a direction perpendicular to the stack of stacks. In this way, the stress acts perpendicular to the combined elements and / or individual elements. The vibrational stress g is preferably applied in a direction parallel to the stack or the elements to be combined and / or the individual elements.
要素は、強化繊維および未硬化樹脂マトリックスを含み得る。繊維は、好ましくは、マトリックスが予備含浸されプリプレグを形成する。 The element can include reinforcing fibers and an uncured resin matrix. The fibers are preferably pre-impregnated with a matrix to form a prepreg.
好ましくは、応力は、連続的に、同時にまたは周期的に加えられる。 Preferably, the stress is applied continuously, simultaneously or periodically.
さらなる態様において、温度処理および応力印加は、少なくとも部分的に同時に起こる。それらはまた、温度処理および／または応力印加の１つ以上のサイクルの、連続的および／または周期的な方法で印加され得る。サイクルは、要素が分離されるまで、繰り返され得る。 In a further aspect, the temperature treatment and stress application occur at least partially simultaneously. They can also be applied in a continuous and / or periodic manner in one or more cycles of temperature treatment and / or stress application. The cycle can be repeated until the elements are separated.
好ましくは、応力印加は、温度処理に続く。我々は、これが、要素を分離するのに成功する方法を提供することを見出した。 Preferably, the stress application follows the temperature treatment. We have found that this provides a way to succeed in separating elements.
さらなる態様において、温度処理は、個々にマトリックスを加熱または冷却することによって、樹脂マトリックスのＴｇ（ガラス転移温度）を増加または減少させる。我々は、−８０〜１０℃、好ましくは、−６０〜７℃、−４０〜５℃、−３０〜３℃、−２０〜０℃の低下した温度での応力ａ〜ｇの印加、および／または上述の温度の組み合わせは、組み合わせられる要素および／または個々の要素を分離する有効性を高めることを見出した。低下した温度は、樹脂マトリックスのＴｇを低下させる。 In a further embodiment, the temperature treatment increases or decreases the Tg (glass transition temperature) of the resin matrix by individually heating or cooling the matrix. We apply stress ag at reduced temperatures of −80 to 10 ° C., preferably −60 to 7 ° C., −40 to 5 ° C., −30 to 3 ° C., −20 to 0 ° C., and / or Alternatively, the temperature combinations described above have been found to increase the effectiveness of separating the combined elements and / or individual elements. The reduced temperature reduces the Tg of the resin matrix.
別の態様において、温度処理は、−３０〜１０℃、または−２０〜５℃、または−１０〜０℃、または−５〜０℃および／または上述の温度の組み合わせの範囲の温度に、樹脂マトリックスを冷却することを含む。マトリックスの冷却は、樹脂マトリックスタックを低下させる効果を有する。我々は、これがまた、分離の有効性を増加させることを見出した。 In another embodiment, the temperature treatment is performed at a temperature in the range of −30 to 10 ° C., or −20 to 5 ° C., or −10 to 0 ° C., or −5 to 0 ° C. and / or combinations of the above temperatures. Cooling the matrix. The cooling of the matrix has the effect of reducing the resin matrix tack. We have found that this also increases the effectiveness of the separation.
樹脂マトリックスは、冷却されて、室温で樹脂のタック値の４０％未満、または３０％未満、または２０％未満、または１０％未満、または好ましくは５％未満の値に樹脂のタックを低減させ得る。樹脂のタック値またはタックは、ツール表面またはアセンブリ内の他のプリプレグプライに対する樹脂の接着の大きさである。タックは、「Ｅｘｐｅｒｉｍｅｎｔａｌ ａｎａｌｙｓｉｓ ｏｆ ｐｒｅｐｒｅｇ ｔａｃｋ（プリプレグタックの実験的分析）」Ｄｕｂｏｉｓら, （ＬａＭＩ）ＵＢＰ／ＩＦＭＡ, ２００９年３月５日で開示される方法に従って、樹脂自体またはプリプレグとの関係で測定され得る。この刊行物は、タックが、そこに記載されているような装置を使用することによって、３０Ｎの初期圧力で、３０℃の一定温度で樹脂またはプリプレグを接触させるプローブの最大剥離力を測定することによって、客観的かつ反復可能に測定されることができ、これは、続いて５ｍｍ／分の速度で動かされることを開示する。これらのプローブ接触パラメータについて、樹脂に対するタックＦ／Ｆｒｅｆは、０．１〜０．６の範囲であり、Ｆｒｅｆ＝２８．１９ＮおよびＦは、最大剥離力である。プリプレグについて、タックＦ／Ｆｒｅｆは、０．１〜０．４５の範囲であり、Ｆｒｅｆ＝２８．１９ＮおよびＦは、最大剥離力である。 The resin matrix can be cooled to reduce resin tack to a value of less than 40%, or less than 30%, or less than 20%, or less than 10%, or preferably less than 5% of the resin tack value at room temperature. . Resin tack value or tack is a measure of the adhesion of the resin to the tool surface or other prepreg plies in the assembly. Tack was measured in relation to the resin itself or prepreg according to the method disclosed in “Experimental analysis of prepreg tack”, Dubois et al., (LaMI) UBP / IFMA, March 5, 2009. Can be done. This publication measures the maximum peel force of a probe that contacts a resin or prepreg at a constant temperature of 30 ° C. at an initial pressure of 30 N by using an apparatus such as that described in Tac. Can be measured objectively and repeatably, which discloses that it is subsequently moved at a speed of 5 mm / min. For these probe contact parameters, the tack F / Fref to the resin is in the range of 0.1-0.6, and Fref = 28.19 N and F are the maximum peel forces. For the prepreg, the tack F / Fref is in the range of 0.1 to 0.45, and Fref = 28.19 N and F are the maximum peel forces.
別の態様において、温度処理は、樹脂マトリックスの加熱を含む。加熱は、樹脂マトリックスの粘度を低下させる効果を有する。 In another embodiment, the temperature treatment includes heating the resin matrix. Heating has the effect of reducing the viscosity of the resin matrix.
樹脂マトリックスを加熱して、室温（２０℃）で、樹脂のタック値の６０％未満、好ましくは４５％未満である値に樹脂の粘度を低下させ得る。 The resin matrix can be heated to reduce the viscosity of the resin at room temperature (20 ° C.) to a value that is less than 60%, preferably less than 45% of the tack value of the resin.
温度処理および／または応力の印加は、同時に、部分的に同時に、続いて、または周期的に実施され得るものであり、その間温度および／または印加される応力が変化しうる。温度処理および／または応力印加は、要素が分離されるまで、継続され得る。 The temperature treatment and / or application of stress can be performed simultaneously, partially simultaneously, subsequently, or periodically, during which temperature and / or applied stress can vary. Temperature treatment and / or stress application can be continued until the elements are separated.
別の態様において、スタックは、樹脂マトリックス（プリプレグ）で予め含浸された繊維強化材料の層の未反応成形体または積層体および／または樹脂含浸された刻んだ強化繊維から形成される成形体および／またはそれらの組み合わせから形成される。要素は、プリプレグを含み得る。 In another embodiment, the stack is formed from unreacted molded bodies or laminates of layers of fiber reinforced material pre-impregnated with a resin matrix (prepreg) and / or molded reinforced fibers impregnated with resin and / or Or a combination thereof. The element can include a prepreg.
さらなる態様において、複合要素が提供され、各要素は、強化繊維および樹脂マトリックスを含み、前記要素は、要素を分離するための温度処理および応力印加の後、結合要素のスタックから形成される。 In a further aspect, composite elements are provided, each element comprising a reinforcing fiber and a resin matrix, said element being formed from a stack of bonded elements after temperature treatment and stress application to separate the elements.
スタックは、樹脂マトリックスで予め含浸された繊維強化材料の層（プリプレグ）の成形体または積層体および／または樹脂含浸された刻まれた強化繊維から形成される成形体および／またはそれらの組み合わせの切断の後に形成され得る。 A stack is a cut of a molded body or laminate of fiber reinforced material layers (prepregs) pre-impregnated with a resin matrix and / or molded bodies formed from resin-impregnated engraved reinforcing fibers and / or combinations thereof. Can be formed after.
１つの態様において、成形体は、複数の要素を含んでもよく、各要素は、強化繊維および樹脂マトリックスを含み、前記要素は、上記のような方法のいずれかに従って、スタックを分離することによって形成される。 In one embodiment, the molded body may comprise a plurality of elements, each element comprising a reinforcing fiber and a resin matrix, said elements being formed by separating the stack according to any of the methods as described above. Is done.
スタックは、複数の要素に分離する前に、より小さなスタックに切断され得る。あるいは、またはさらに、分離された要素は、それらの分離後、より小さな要素に切断され得る。 The stack can be cut into smaller stacks before separating into multiple elements. Alternatively or additionally, the separated elements can be cut into smaller elements after their separation.
発明の詳細な説明
本発明を、以下の図面を参照して、単なる例示として記載する。
DETAILED DESCRIPTION OF THE INVENTION The present invention will now be described by way of example only with reference to the following drawings.
積層体レイアップは、樹脂マトリックスで含浸される繊維強化の結合される層から形成されることができる。好ましくは、繊維強化層は、一方向繊維トウを含み、層は、準等方性レイアップを形成する互いに関連して配置される。好ましくは、層は、＋９０／＋４５／０／−４５／−９０方向に延びており、それらは、それらの倍数に配置され得る。 Laminate layups can be formed from fiber reinforced bonded layers impregnated with a resin matrix. Preferably, the fiber reinforced layer comprises unidirectional fiber tows and the layers are arranged relative to each other to form a quasi-isotropic layup. Preferably, the layers extend in the + 90 / + 45/0 / −45 / −90 direction and they can be arranged in multiples thereof.
これらのレイアップは、圧縮成形体としてその後加工される積層体部品に（ダイ）切断され得る。切断プロセスは、余剰な積層体レイアップ材料をもたらす。この余剰な材料は、別の目的のために使用可能であり、本発明は、これに対処し、並びに一般的に改善を提供することを目指す。 These layups can be (die) cut into laminate parts that are subsequently processed as compression molded bodies. The cutting process results in excess laminate layup material. This surplus material can be used for other purposes, and the present invention aims to address this and provide improvements generally.
図１は、再利用プロセス１０を示す。ダイカット積層プリプレグシートからのオフカット１２は、より小さい積層体要素１４に切断され、またはそれらは、プロセス１０の完了後に切断され得る。これらの要素は、加熱または冷却のいずれかにって、または両方の温度処理の組み合わせによって、温度処理される１６、１８。加熱１８は、樹脂の粘度を低下させ、Ｔｇを増加させ、分離を助けることができるが、冷却は、樹脂マトリックスのＴｇおよび／またはタックを減少させ、層をより容易に分離させる。 FIG. 1 shows a reuse process 10. Offcuts 12 from the die cut laminated prepreg sheets can be cut into smaller laminate elements 14 or they can be cut after completion of process 10. These elements are temperature treated 16, 18 either by heating or cooling, or by a combination of both temperature treatments. While heating 18 can reduce the viscosity of the resin and increase the Tg and aid in separation, cooling reduces the Tg and / or tack of the resin matrix and makes the layers more easily separated.
温度処理後、要素は応力２０の印加によって、分離される。応力は、積層体要素に対して異なる方向および／または形態で加えられ得る。ステップ２０、１６および１８は、要素が分離されるまで、部分的に同時にまたは周期的に組み合わせられるか、または実行され得る。分離２０の後、ランダムに分布した単一層プリプレグ要素２２は、シート成形複合体（ＳＭＣ）２４としてシート形態に一緒に組み合わされる。次に、このＳＭＣは、複合部品を製造するための再利用に適している。 After temperature treatment, the elements are separated by the application of stress 20. Stress can be applied in different directions and / or configurations to the laminate element. Steps 20, 16 and 18 may be combined or performed partially in parallel or periodically until the elements are separated. After separation 20, randomly distributed single layer prepreg elements 22 are combined together in sheet form as a sheet molding composite (SMC) 24. The SMC is then suitable for reuse to produce composite parts.
したがって、上記に記載されるような方法およびモールディング複合体が提供される。 Accordingly, methods and molding complexes as described above are provided.
Claims (16)
ａ．曲げ応力
ｂ．ねじり応力
ｃ．圧縮応力
ｄ．せん断応力
ｅ．剥離応力
ｆ．引張応力
ｇ．振動応力。 The method of claim 1, wherein the applied stress is selected from one or more of the following stresses:
a. Bending stress b. Torsional stress c. Compressive stress d. Shear stress e. Peel stress f. Tensile stress g. Vibration stress.
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| EP14183087.7 | 2014-09-01 | ||
| PCT/EP2015/069380 WO2016034451A1 (en) | 2014-09-01 | 2015-08-24 | Moulding material and method of forming same |
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| US4002877A (en) * | 1974-12-13 | 1977-01-11 | United Technologies Corporation | Method of cutting with laser radiation and liquid coolant |
| GB2168002B (en) * | 1984-12-06 | 1988-06-08 | Rolls Royce | Composite material manufacture |
| US4639572A (en) * | 1985-11-25 | 1987-01-27 | Ibm Corporation | Laser cutting of composite materials |
| US4908494A (en) * | 1988-03-18 | 1990-03-13 | United Technologies Corporation | Method for stabilized cutting of fibrous composite preforms |
| DE4421415C1 (en) * | 1994-06-18 | 1995-09-21 | Deutsche Forsch Luft Raumfahrt | Detaching a film from adhesive bonded underlay |
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| JPH0994476A (en) * | 1995-03-02 | 1997-04-08 | Daimler Benz Ag | Method for recovering plastic from fragment of composite material |
| JP2002212320A (en) * | 2001-01-23 | 2002-07-31 | Toray Ind Inc | Prepreg and very low temperature tank |
| JP2003277532A (en) * | 2002-03-27 | 2003-10-02 | Toray Ind Inc | Prepreg and tubular product made of fiber reinforced composite material |
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